Nozzle



Oct, 6, 1959 R. L. CUMMINGS NOZZLE 2 Sheets-Sheet 1 Filed April 10, 1956[I7 V5717 2271* Rose/Fr L Cl/MM/Nsd 51/575;

M A WW I. a a m E W E a s I P m. mm 3 main and after burner assemblyfuel nozzles.

Unie rates P fi fi NOZZLE Robert L. Cummings,Berea, Ohio, assiguor toThompson Ramo Wo'oldridge 'IIlC-, a corporation of Ohio This inventionrelates to a fluid atomizing nozzle. Specifically, this inventionrelates to a vaporous fuel atomizing nozzle in which pressurizedvaporous fuel is utilized as the atomizing gas to obtain a finerdispersion of liquid fuel particles.

The current development in turbojet engine fuel cooling systems, such asare employed to cool hot lubricating engine oil, has resulted intheproduction of a hot vaporous fuel byproduct, which has been utilized asa supple ment to the conventional liquid fuel flow through the As anincident of the use of vaporous fuel to supplement the main liquid fuelsystem, it has been foundthat the hot vaporous jfuelbyproduct such as isgenerated ,by fueloil heat exchangers, could also be used to perform thesame function as compressed bleed .air as a means of inducingatomization of the liquid fuel passing through the main and after burnerfuel nozzles.

Several important advantages are realized from the substitution ofvaporous fuel for compressed bleed air in the atomizing nozzles, namely,a more efiicient cornbustion of the fuel is obtained, and thevaporousfuel such as is generated by a typical fuel oil heat exchangeris at a sufficiently high pressure topermit a direct utilization in themaincombusionchamber burners or after burners,

without additional pressurization. The latter mentioned advantagecorrespondingly results in a simplification of theplumbing andassociated control systems, .with a ,cor-

respondingreduction in weight and unit co-st of the system.

The present invention discloses one means of beneficially exploiting thepressurized vaporous fuel by-productof a typical fuel oil heatexchanger, in the form of a vapor atomizing fuel nozzle, in which thehot pressurized vaporous fuel is utilized to augment atomizati on anddispersion of liquid fuel that is being sprayed into ,themain combustionchamber or through theafter burner nozzles.

Briefly described, the present invention contemplates a nozzle structurehaving a liquid fuel passage and a vaporous fuel passage. Liquid fuelorifices are provided to initially meter the liquid fuel supply intoafine stream or vortex of discrete particles. A vaporous fuelsorifice is.also provided to direct an intersecting jet or flow of pressurizedvaporous fuel .intoand through the streamer vortex of liquid fuel, tothereby disperse and ,atomize the liquid fuel flow. i i z The nozzlestructureof thepresent invention also contemplates a means formaintaining a unidirectional. metered flow of hot vaporous fuel, therebyassuring a proportionate flow of atomized fuel from the nozzleand theprevention of -any.reverse flow of vaporous fuel or flame flash back,during periods of low vapor fuel pressure. i

2,907,527 fatented Oct. 6, .1959

"ice

vide an, improved typeof atomizing fuel nozzle which utilizespressurized vaporous fuel as the atomizing gas.

A further object of the present invention is to improve the combustionefiiciency of a turbojet engine, or other internal combustion engineutilizing a liquid fuel, by augmenting the atomization of the liquidfuel through the impingement of an intersecting jet of hot vaporous fuelinto a flowoftheliquid fuel.

A still further object of the present invention is to effectivelyutilize the hot vaporous fuel by-product of a typical fuel-heatexchanger in a turbojet engine, in the form of augmenting theatomization of liquid fuel in the burners of a turbojet engine.

Many other objects and advantages of the present invention will becomemanifest to those versed in the art upon making reference to thedetailed description which follows and the accompanying sheets ofdrawings.

On the drawings:

Figure l is a schematic elevational view of a turbojet engine .andvaporous fuel producing fuel-oil heat exchanger, in whichthe hot.vaporous fuel byproduct is utilized to augment vaporization of theliquid fuel in the burners of the engine, according to the principles ofthe present invention.

[Figure 2. is. an enlarged cross-sectional view, with parts inelevation, of a variable area vapor atomizing fuel nozzle, according tothe principles of the present invent n; and

Figure 3 is an enlarged cross sectional view, with parts in elevation ofa swirl type variable area vapor atomizing nozzle, according to theprinciples of the present invention . a ,turbojet engine E.

The turbojet engine E, is comprised generally of an eng i 'ne bo dy 10which includes an inlet 11, acompressorstator vane assembly 12, aturbine wheel rotor-stator vane assembly 113, a diffusercone 14, and adischarge tail pipe 16. compressor rotor assembly 17 is enclosed by theturbine body 10 and comprises a Compressor rotor vane assembly 18,drive'shaft 19, and a turbine wheel 20. A

plurality of combustors 21 are positioned between the compressorassembly 18 and turbine wheel 20, and con- ,tain :a plurality .of vaporatomizingnozzleassemblies 7A, which supply a pressurized flow of highvelocity air and liquid fuel tothe combustors 2 1, preparatorytoignition.

.Ihfi Compressor rotor assembly 17 is suitably journaled, for example,by a bearing assembly 23, and a connecting oil conduit .24 maintains aflow of cool lubricating In addition to the .economic advantagesresulting from .the present invention, greater fuel combusion chamber.efiiciencieswill betrealized, as a result .of the impingeoil to therespective bearing assemblies 23.

,An,. after burner nozzle assembly 26 ,is positioned in a downstreamdiffusion passage 27 to augment thrust from the enginerE, during.emergency flight conditions, or whenever additional thrust is required.

The oil cooling system for the turbojet engine E, is

comprised generally of a hot oil outlet conduit 28, which receives a howof hot lubricating oil from anoutlet 29 on the engine body 10. Thehotoil conduit 28 supplies hot engine lubricating .oil to .a boilingcooler 30.

The boiling cooler 30 receives a flow of hot .oil from a conduit 28 anddischarges cool oil through a conduit syscooled 'oil from the conduit 31and discharges cold oil through a conduit 37 to a cool oil return inlet38 on the engine body 10.

The fuel-oil heat exchanger 36, includes an internal heat transferconduit system 39 which permits a transfer of thermal energy from thehot oil to surrounding cool fuel.

A conduit 40 supplies the cool fuel to the heat exchanger 36, and adischarge conduit 41 delivers heated fuel to the burner assembly 22 inthe engine E.

A thermal sensing unit '42 on the conduit 41, selectively activates athrottle valve 43 which permits a bypass fiow of hot fuel from theconduit 41.through the by-pass conduit 32 to the boiling cooler 30,whenever the fuel temperature in the conduit 41 reaches a predeterminedmaximum value. a

The fuel oil heat exchanger 36, receives a flow of cooled fuel throughthe conduit 40 from a connecting conduit 44 and fuel tank T.. A mainpump P, n1aintains a flow of fuel from the fuel tank T, througha fuelcontrol assembly 46 to the fuel oil heat exchanger 36.

When the temperature of the fuel in the conduit 41 rises to a sufiicientvalue to activate the bypass throttle "valve 43, the hot lubricating oilin the boiling cooler 30,

will vaporize the hot fuel in the heat transfer passages The liquid fuelfitting 56 is transversely intersected by a main liquid fuel flowconduit 59 which supplies a flow of pressurized liquid fuel to a liquidfuel chamber 60 which is formed between the liquid fuel conduit 51 andstarting liquid flow conduit 58. The flow of liquid fuel through thestarting conduit 58 is initiated and regulated by a suitable controldevice, not shown.

The nozzle body 50 is internally threaded as at 61 to receive a vaporousfuel flow fitting member 62 which is provided with a plurality ofvaporous fuel discharge flow passages 63. These passages can be aplurality of bores such as from 4 to 12 bores in the fitting 62. Thevaporous fuel passages 63 are in communication with the vaporous fuelchamber 52, and form a flow conduit for vaporous fuel delivered by theconduit 53.

An annular bellows assembly 64 circumscribes the vaporous fuel flowfitting member 62, and has one end 7 secured to the fitting and theother endprovided with an integral lip portion 66 overlying thedischarge end of the fitting to selectively close the vaporous fuel flowpassages 63. A radiation shield 67 encloses the bellows assembly 64, andcooling air louvers such as 68 are I, provided on the shield to divert acirculating flow of combustion chamber air around the bellows assembly'64and radiation shield 67 to prevent excessive heating of the bellowsassembly 64 and other parts of the nozzle A It will be understood thatwhen the vapor pressure in passages 63 is great enough to stretchthebellows 64,

34, from which the hot vaporous fuel will be withdrawn from the boilingcooler 30 through the connecting con duit 33, by a vapor pump'47.

The vapor pump 47 is driven, for example, by an electric motor M, andwithdraws and recompresses vaporous fuel from the heat transfer passages34 in the boiling cooler 30, and selectively delivers a pressurized flowof hot vaporous fuel through a conduit 48 to the main burner vaporatomizing fuel nozzle assemblies A. A control valve assembly 49 isprovided in the conduit 48 to control the flow of hot vaporous fuel tothe nozzle assembliesA.

Thus it will be appreciated that the fuel-oil heat exchanger system,shown in Figure 1, while primarily serving to cool thehot lubricatingoil from the engine E, incidentally produces a hot pressurized vaporousfuel byproduct, which, according to the present invention, iseffectively utilized to augment the atomization of the liquid fueldelivered by the main burner nozzle assemblies A.

It should further be appreciated, that while I have illustrated atypical turbojet engine fuel-oil heat exchanger system as a source forproducing pressurized vaporous fuel, any other system having a hotpressurized vaporous fuel by-product could be utilized to practice theprinciples of my invention.

Referring now to Figure 2, a more detailed view of the combinationliquid and variable area vapor atomizing fuel nozzle A of Figure l, isillustrated, such as is utilized in the main combustors 21 in theturbojet engine E, shown in Figure l. 7 The liquid vapor atomizing fuelnozzle A, is comprised of a generally hollow nozzle body 50 in which isformed .a concentric liquid fuel conduit 51. An annular vaporous fuelchamber 52 is thus formed between the nozzle body 50 and concentricliquid fuel conduit 51. An intersecting conduit 53 in the nozzle body50, supplies pressurized fuel to the chamber 52.

The cylindrical liquid fuel conduit 51 is internally threaded as at 54to receive a liquid fuel flow fitting 56.

the lip 66 will be shifted toward the open'end of the shield 67 and aflow path around the bellows inthe shield from'the louver openings tothe open end of the shield is created. The atomized stream from thenozzle will aspirate air through this path to cool the end of the nozzleA.

The downstream end of the main liquid fuel passage -60 and startingliquid flow conduit 58, are closed by a The liquid fuel'flow fitting 56is axially bored as at 5 7 to receive a liquid fuel starting conduit 58.

flow plug member 69. The flow plug member 69 is provided with aplurality of circumferentially spaced axial fiow orifices whichcommunicate withthe main liquid fuel chamber 60. A centrally disposedstarting flow orifice 71 communicates with liquid fuel in the startingconduit 58 to provide a metered flow of liquid fuel during starting.

The downstream faces of the vaporous fuel flow fitting member 62 andorifice plug member 69 are conically tapered to form a surface 72 whichdetermines the corresponding angular relationship of the lip 66 to thevaporous fuel flow passages 63.

Itshould be noted that the angular relationship of the lip 66 andco-planar surface 72 is such that when a sufiicient fuel vapor pressureis obtained in the chamber 52 to unseat the lip 66, a flow ofpressurized vaporous fuel will issue out of the vaporous fuel passages63 and be deflected centrally inwardly toward fine liquid fuel streamsissuing from the orifices 70. The angular position of the lip 66 is suchas to divert the vaporous fuel streams from the flow passages 63 intoanroptimum intersecting path with the fine streams of liquid fuelissuing from the flow orifices 70 and 71, to obtain optimum atomizationand dispersion of the liquid fuel.

It will thus be appreciated that the bellows assembl 64 and lip 66 forma combination check valve, flow regulator, and deflecting surface forthe vaporous fuel flow, whichpermits a high degree of control as to theflow rate and atomization of pressurized liquid fuel passing through theflow orifices 70 and 71.

Referring now to Figure 3, an alternative swirl type variable area vaporatomizing fuel nozzle B, is illustrated, which is comprised generally ofa hollow cylindrical nozzle body 73 having an internally threadedportion 74 to ,position and retain a vaporous fuel flow meteringassembly b, the nozzle body 73 beingclosed at .one end by a cap 76 andhaving an inturned beveled lip 75'. A pressurized liquid fuel conduit 78and vaporous fuel conduit 79, intersect a sidewall of the nozzle body 73to deliver a'pressurized flow'of liquid and vaporous fuel to the nozzleassembly B.

A centrally disposed liquid-vaporous fuel mixing assembly c ispositioned in the hollow nozzle body 73 abutting the lip 77, and iscomprised generally of a thimble member8ti, acooperatively abuttingvariable area vaporous fuel jet flow passage member 81 and aliquidvaporous fuel flow assembly retaining member 82.

The thimble-shaped liquid-vaporous fuel mixing member 80, includes abeveled end portion 83 which engages the lip 77 on the nozzle body '73to retain and centrally position the liquid-vaporous fuel mixingassembly 0 in the nozzle body 73.

The dome end of the thimble 80 has an outwardly flared discharge orificeopening 84 therethrough and an extended skilt portion 36, whichcircumferentially engages the fiow passage forming member 81 around areduced diameter end portion 87 to form a centrally dis- 'posed liquidfuel swirl chamber 88 therebetween.

A plurality of circumferentially spaced liquid fuel orifices 89 in theskirt portion" 86 of the liquid-vaporous fuel mixing member 80 feed aswirling flow of pressurized liquid fuel from a liquid fuel chamber 90formed between the liquid vaporous fuel mixing assembly 0 and nozzlebody 73 to the swirl chamber 88. The orifices 89 preferably havetangential outlets to establish a rotation or swirl of fuel in thechamber 38. An annular O-ring seal assemblySS prevents any leakage ofpressurized liquid fuel from the chamber 96 between the vaporous fuelflow passage member 81 and nozzle body 73, The fuel discharge orifice 84is in communication with the liquid fuel swirl chamber 88, and receivesa fine stream or atomized fluid flow therethrough.

The vaporous fuel flow passage member 81 is provided with a centrallydisposed vaporous fuel flow passage 91, which includes an axiallyconvergent bore 92 and an axially divergent bore 93 from a centrallydisposed throat 94. The vaporous fuel flow passage 91 is incommunication with the liquid fuel swirl chamber 88 and in axial flowalignment withthe discharge orifice 84, thus permitting asubstantiallyuninterrupted axial jet flow of pressurized vaporous fuelthrough the swirl chamber 88 and discharge orifice 84.

The liquid fuel mixing member 80 and vaporous fuel flow passage member81 are axially positioned in the nozzle body 73 by the retaining member52. The retaining member 82 is provided with a plurality of axiallyextending vaporous fuel passages 96 which are in communication with thevaporous fuel chamber formed by the retaining member 82;, nozzle body73, cap 76 and flow metering assembly 15. The retaining member $2 isbored as at 98 to slidably journal a shaft portion 99 of a flow meteringneedle valve assembly 100 which is ,reciprocably positioned in thethroat 94 of the vaporous fuel flow passage 91.

Thus it will be appreciated that the needle valve assembly ltlilprovides a variable flow of vaporous fuel through the flow passage 91,swirl chamber 88 and flow discharge orifice 77, by varying the area ofthethroat 94 in response to the degree of axial movement of the needlevalve assembly 109.

The vaporous fuel flow metering assembly I), is comprised of the needlevalve assembly 100, a bellows 101, between the valve'and cap76, and acoil spring 162. The flow needle valve assembly 100includes a flangedend portion 103 receiving one end of the bellows thereover, and anannular spring retaining sleeveltM centeringthe coil spring 102. Arecess 1% is formed in the cap 76 to retain the coil spring 192 in axialoperative alignment with the needle valve assembly 190.

A passage 107 is formed in the cap 76, to communicate pressure from somedownstream point of utilization a 6 tea chamber 108 formed by the needlevalve assembly 100, bellows 101 andclosure cap76.

The compression rating of the coil spring 102 is sufficiently high tourge the needle valve assembly 100 into an axially closed position inthe throat 94 of the vaporous fuel flow passage 91, whenever vaporousfuel pressure falls below a predetermined minimum value, or below thereference pressure in the chamber 108.

It will further be appreciated that the proportionate axial movement ofthe needle valve assembly 1100 in the throat 94 provides a variable areaflow orifice which permits a substantially uniform flow of vaporous fuelthrough the flow passage 91, even during periods of low liquid fuel flowrate, which produces a finely atomized mist or stream of atomized fuelthrough the orifice 84, due to the shearing action of the high velocityjet of vaporous fuel through the liquid fuel vortex in the swirlchambertili.

By way of operative summary of the nozzle assembly B, pressurized liquidfuel is supplied to the liquid fuel chamber 9% in the nozzle assembly Bthrough the liquid fuel conduit 78. Liquid fuel in the chamber is thencommunicated through the orifices 89 in the vaporous liquid fuel mixingmember 81 to the swirl chamber 88.

Pressurized vaporous fuel is supplied to a pressure responsive chamber97 from which it is communicated through the flow passages 96 in theretaining member 82, through the variable area throat 94 of the vaporousfuel flow passage 91. In addition, pressurized vaporous fuel in thechamber 97 acts on the flange 103 to compress the coil spring 1&2 in thechamber 1&8 and collapse the bellows 191.

Reference pressure from some point of utilization is communicatedthrough the passage 107 to the chamber 1%, to thereby exert an opposingforce in addition to the compression of the coil spring M2 to axiallyurge the needle valve assembly into a closed position in the throat 94,whenever the vaporized fuel pressure in the chamber 97 falls below acertain predetermined minimum value.

It will thus be appreciated that the degree of axial movement of theneedle valve assembly Mill, and corresponding change in orifice area atthe throat 94 ofthe vapor fiow passage 91, is controlled'as a functionof the differential pressure between the vaporous fuel in the chamber 97and the combined pressure of the coil spring 102 and the referencepressure from the point of utilization in the chamber 108.

Vfhile only two embodiments of the present invention have been describedin Figures 2 and 3 it should be understood that many other modificationsand variations may be effected Without departing from the scope of thenovel concepts herein disclosed.

I claim as my invention:

1. A swirl type fuel nozzle structure comprising a nozzle body having aflow orifice formed therein, said nozzle body including a liquid fuelchamber, conduit means delivering pressurized liquid fuel to said liquidfuel chamber, said liquid fuel chamber supplying pressurized liquid fuelto a swirl chamber provided by said nozzle body, said swirl chamberbeing in communication with said how orifice, said nozzle body alsohaving a fuel vapor chamber formed therein, conduit means deliveringpressurized vaporous fuel to said fuel vapor chamber, and a connectingpassage directing a jet of pressurized fuel vapor through said swirlchamber and flow orifice, to thereby atomize and disperse said liquidfuel into a finely divided spray.

2. A swirl type fuel nozzle structure comprising a nozzle body having afiow orifice formed therein, said nozzle body including a liquid fuelchamber, conduit means delivering pressurized liquid fuel to said liquidfuel chamber, said liquid fuel chamber supplying pressurized liquid fuelto a swirl chamber provided by said nozzle body, said swirl chamberbeing in communication with said flow orifice, said nozzle body alsohaving a fuel vapor chamber formed therein, conduit means deliveringpressurized vaporous fuel to said fuel vapor chamber, a connectingpassage directing a jet of pressurized fuel vapor through said swirlchamber and flow orifice, and means for regulating the flow of saidpressurized fuel vapor through said swirl chamber and flow orifice toatomize said liquid fuel.

3. A swirl type fuel nozzle structure comprising a nozzle body having aflow orifice formed therein, said nozzle body including a liquid fuelchamber, conduit means delivering pressurized liquid fuel to said liquidfuel chamber, said liquid fuel chamber supplying pressurized liquid fuelto a swirl chamber provided by said nozzle body, said. swirl chamberbeing in communication with said flow orifice, said nozzle body alsohaving a fuel vapor chamber formed therein, conduit means deliveringpressurized vaporous fuel to said fuel vapor chamber, a connectingpassage directing a jet of pressurized fuel vapor through said swirlchamber and flow orifice, a slidable needle valve assembly cooperativelypositioned in said connecting passage to meter the flow rate of saidpressurized fuel vapor a pressure responsive means secured to saidneedle valve assembly controlling the amount of movement thereof, andmeans referencing pressure from a point of utilization of said fuel tosaid pressure responsive means to thereby control the flow of saidpressurized fuel vapor through said swirl chamber and prevent a reversalin flow direction during periods of relatively low fuel vapor pressure.

'4. A nozzle structure adapted to atomize a liquid by utilizing a flowof pressurized vapor of the liquid to be atomized comprising a nozzlebody having a liquid chamber and a vapor chamber, said liquid chamberhaving a plurality of annularly arranged liquid flow orifices incommunication therewith, said vapor chamber having at least one variablearea vapor metering orifice in communication therewith and positioned todirect a flow of vapor to intersect a flow of liquid from said liquidorifices, means positioned to controllably vary the flow area throughsaid vapor metering orifice, and means connected to said vapor chamberand responsive to the pressure of said vapor and connected to saidorifice flow area control means for varying the flow area of said vapormetering orifice to direct a controlled intersecting flow of vapor intojets of said liquid discharging from said liquid orifices and to controlthe flow rate of said vapor and prevent a backflow thereof.

5. A nozzle structure adapted to atomize a liquid by utilizing apressurized flow of vapor of the liquid to be atomized comprising agenerally cylindrical cup-shaped nozzle body having a liquid and a vaporpassage, conduit means supplying pressurized liquid and vapor of saidliquid to said liquid and vapor passages, respectively, a vapor flowfitting member having a plurality of annularly arranged longitudinallyextending vapor flow orifices formed therein carried in the open end ofsaid cup-shaped nozzle body, a plug member having a plurality ofannularly arranged longitudinally extending liquid flow orifices formedtherein carried in the open end of said nozzle body and circumscribed bysaid vapor flow fitting member, said flow fitting member and plug memberhaving their end faces outwardly conically tapered, a combinationbellows check valve and flow regulator member carried by said vapor flowfitting member and having an annular conically tapered deflection lipformed therewith congruently engageable with the conically tapered endfaces of said vapor flow fitting member and plug member to preventreverse flow through said vapor flow orifices when engaged therewith,said deflection lip also being operable to deflect a vapor flow fromsaid vapor orifices into jets of liquid flowing from said liquidorifices to cause atomization thereof and to vary the area of said vapororifices to control the flow rate therethrough, a shield carried on theopen end of said nozzle body enclosing said vapor flow fitting membergand said plug member 'to protect said members from high ambienttemperatures, and louvers on said shield forjcirculating cool fluidthrough said shield and around said vapor flow fitting 'member and plugmember to cool the same.

6. A nozzle structure comprising a nozzle body having a liquid passagemeans formed therein, conduitmeans supplying pressurized liquid to saidliquid passage means, liquid fiow orifices connected to said liquidpassage emitting streams of liquid, vapor conduit means conducting aflow of vapor, orifice means leading from said vapor conduit andpositioned to direct a flow stream of vapor intersecting said liquidstreams, valve means controlling the flow of vapor, and a pressureresponsive valve operator connected to said valve means and opening withvapor pressure and biased to automatically close with'an absence ofvapor pressure and prevent reverse flow of liquid through said vapororifice means.

7. A fuel supply system for a combustion chamber or the like comprisinga liquid fuel conduit, means connected to said conduit for supplyingpressurized liquid fuel thereto, a gaseous fuel conduit, means connectedto said gaseous fuel conduit for supplying pressurized gaseous fuelthereto, a nozzle member having a liquid fuel chamber connected to saidliquid fuel conduit, a gaseous fuel chamber connected to said gaseousfuel conduit, a plurality of small spaced liquid fuel outlets connectedto said liquid fuel chamber and positioned to dispense separated streamsof finely divided liquid particles, and a vapor dispensing means havinga vapor outlet spaced from said liquid fuel outlets and connected tosaid gaseous fuel conduit, said vapor outlet positioned to emit a streamof vapor in a path to intersect said streams of liquid and cause them tobreak up into finer particles and mix with the vapor. v

8. A fuel supply system for furnishing fuel in a combustible form to acombustion zone comprising a first liquid fuel supply conduit forconnection to a supply of fuel, a pressure pump in said supply conduit,a second fuel conduit for supplying fuel in gaseous form for connectionto a source of liquid fuel, a heater converter in said second conduitconverting the liquid fuel to a gaseous fuel, pump means in said secondfuel conduit downstream of said heater converter for pressurizing saidgaseous fuel, a nozzle body member defining a liquid fuel chambertherein connected to said first fuel conduit and a vaporous fuel chambertherein connected to said second fuel conduit for receiving gaseousfuel, means defining a plurality of annularly arranged liquid fuelatomizing orifices in communication with said liquid fuel chamber andpositioned to direct streams of fuel particles, and means defining avaporous fuel metering orifice in communication with said vaporous fuelchamber and opening in a direction to emit a stream of fuel vaporintersecting the streams of liquid fuel to break up into finer particlesand mix with the vapor.

9. A nozzle structure compfising a nozzle body having liquid passagemeans formed therein, conduit means connected to said liquid passage forsupplying pressurized liquid to said liquid passage means, closure meansfor said nozzle body having a plurality of annularly arranged liquidflow orifices communicating with said liquid passage means, said floworifices directing jets of pressurized liquid from said nozzle body to amixing zone outside of said body, means in said body for directing anintersecting annular flow of pressurized vapor of said liquid directlyinwardly into said jets of pressurized liquid in said mixing zoneoutside said nozzle body to thereby atomize and disperse said liquid,and conduit means connected to said vapor directing means for supplyingvapor thereto.

10. A nozzle structure comprising a nozzle body having a liquid passagemeans formed therein, conduit means connected to said liquid passagesupplying pressurized liquid to said liquid passage means, a liquid fuelflow orifice means having a plurality of liquid fuel openings therein toemit broken streams of liquid fuel into a mixing zone and connected tosaid liquid fuel passage, a plu: rality of annularly arranged openingsfor emitting a flow of gaseous fuel annularly surrounding said liquidfuel orifice means, conduit means connected to said gaseous fuelopenings for supplying fuel thereto, and an annular deflector meanshaving a circular deflector edge positioned to be engaged by saidgaseous fuel emerging from said gaseous fuel openings and for deflectingsaid gaseous fuel into said mixing zone whereby an annular flow streamof gaseous fuel will intersect the stream of liquid fuel to cause amixing and dispersion thereof.

11. A burner and nozzle structure for a combustion zone comprising anozzle body having a liquid fuel passage means formed therein, conduitmeans connected to said liquid fuel passage for supplying pressurizedliquid fuel to the fuel passage means, closure means for said nozzlebody having a plurality of annularly arranged liquid fuel flow orificescommunicating with said liquid fuel passage means, said flow orificesdirecting jets of pressurized liquid fuel from said nozzle body to amixing zone outside of said body, means in said body for directing anintersecting annular flow of pressurized vaporous fuel directly inwardlyinto said jets of pressurized liquid fuel in said mixing zone outside ofsaid nozzle body to thereby atomize and disperse said liquid fuel,conduit means connected to said vaporous fuel directing means forsupplying vaporous fuel thereto, and a liquid starting fuel orifice insaid nozzle closure means centrally located with respect to saidannularly arranged liquid fuel orifices for supplying a starting fuel tothe mixing zone and positioned to direct a jet of starting fuel to beintersected by the annular flow of pressurized vaporous fuel.

References Cited in the file of this patent UNITED STATES PATENTS1,631,007 Bucknam May 31, 1927 2,072,281 Simam'n Mar. 2, 1937 2,162,432Hillhouse June 13, 1939 2,237,842 Reynolds Apr. 8, 1941 2,260,987 DArcyOct. 28, 1941 2,379,979 Michaud July 10, 1945 2,404,081 Mock July 16,1946 2,801,134 Neugebaur July 30, 1957 2,815,069 Garraway Dec. 3, 1957

